Abstract
Modal global instability analyses of viscous, supersonic flow past a circular cylinder is carried out for diameter-based Reynolds number of up to 10000 and Mach number 6. The supersonic base flows are computed by DNS using second-order finite volume and high-order finite difference spatial discretization methods. Unlike previous work which predominantly focused on the separation bubble in the cylinder wake, the flow domain considered in the present instability analysis concentrates on the windward face of the body, that contains both subsonic and supersonic flow; the bow shock also forms an integral part of the analysis. It is suggested that the linear instability mechanisms developing in the domain between the shock and the body surface are conditioned by instabilities generated at the shock itself.
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